Aeroplane



Oct. 2, 1928.

V. CAVALERI AEROPLANE Filed Aug. 20, 1927 3 Sheets-Sheet 1 V. CAVALERIOct. 2, 192st AEROPLANE 3 Sheets-Sheet Filed Aug. 20, 1927 Inventorkw/ff 5am/5w' oct. 2, 192s. 1,686,071

V. CAVALERI AEROPLANE Filed A ug. 2o, 1927 3 sheets-shet 3 i InventorWfcefff al/a/e/v' Patented oci. 2, 192e.

rATENr ortica.

VINCENT CAVALERI, F BROOKLYN, NW YORK.

i. annorLaNn.

Application mea august 2o, 1927.y temi mamada.

The resent invention relates'to improvements 1n aeroplanes and moreparticularly to an improved propulsion unit for aeroplanes and the like,A

An important obj'ect of Ithe'invention resides in the provision of a proulsion unit .Which-sucks in air from the ront of the aeroplane,compresses it, stores it, and ex"- hausts it rearwardly of the aeroplaneas needed for propulsion purposes.

A still further important object of the invention resides in theprovision of a propulsion unit of this nature which is simple in `itsconstruction, comparatively inexpensive l5 to`manufacture, thoroughlyefficient and reliable in use| and operation, -and'otherwise welladapted for the purpose for which it is desi ed. I .ith` the above andnumerous other objects in view aswill appear as the descriptionproceeds, the inventlon resides in 'certain novel features ofconstructiomwand in the combination and arrangement ofl parts as will behereinafter more fully described and claimed. ff)

In the drawing Figure 1 is asectional elevation of an aeroplaneembodying the features of lI ny invention,

Figure 2 is a fragmentary top plan. view thereof, f t,Figure is afragmentary front elevation thereof, and, f Figure 4 is a detail'section through one of the compressors. Referring-to the ,drawing indetail it will be seen that the numeral 5 denotes a fuselage `designedas to the usual well known constructionhaving conventional steeringmpans at o -therear thereof. The nose-of the fuselage "is `preferablypointed and .has intake suction pipes 6 leading rearwardly, onefto eachside of the point and connected to compressorsl f 7 operativelyconectedby suitable gearing above.

wardly for a short distance. All of these' p1pes 14, 15 and 16 havevalves 18' therein controlled in unison by a lever`1 9 convenientlylocated in respect to the drivers seat so that the compressed air 11 maybe exhausted as needed for propelling the aeroplane.

From the above detailed description, it w1ll be seen that I have deviseda very simple and efficient unit for propelling the aeroplane which willcause afrarity of air in/ frontof the aeroplane and a thickness of airin' the rear of the aeroplane so as to push the aeroplane forwardly. Inthis way a great deal of speed may beaccomplished and d angers caused byunexpected eddies, air pockets, and the like will be greatly minimized.It is preferable to construct the -machine with wings or planes 20. Inthe present instance I have shown a single plane. This plane 20 ishollow so as to be -filled with a lighter than air gas such as helium,hy-

drogen, or the like, through a valve 21. It is alsol preferable to mountpontoons 23 on the bottom of the fuselage for;` landing in the waterand" also to obtain maximum buoyancy in the air by making the pontoonshollow and filling the/in through' a valv'e 24 with lighter than air gassuch as mentioned. i

/e 85 It is thought that the construction, oper-y ation, utility, andadvantage. of the inven'- tion will now -be clearly understood without amore detailed description thereof. How- V ever, .I have disclosed inFigure 4 a form. 9o of compressor 7 which may be used whereinthe`cylinder has a piston 26 reciprocable therein by means of a pitman 27yoperated by .an eccentric 28 o'n a shaft 29 from the gearing 8. Checkvalves S30-'and 31 are so arranged that the air may pass kin onedirecltion only, `thus the downward stroke of ther piston will suck theair 'into the cylinder through-the one pipe andthe upward stroke 4Lofthe piston Willexhaust this air through 190 l5 8'with a' prime mover9 such as anfinternal` the other pipe and linally cause acomprescombustion engine. Pipes 10 leadfromr the compressors to astorage tank 11 and these pipes 10 have checkvalves 12 thereim O'utetpipes'14 and 15' and 16 lead from` the 50 front of the tank 11. The pipe1i-leads latorally and then rearwardly to terminate ady 'acent the tailof the fuselage. The pipes 1 5 ead laterally from the tank and terminateintermediate the ends thereof while the p'ipe 55 16 extends forwardlytotheforward portion` of the fuselage, then laterally dnd tlen rear-s sionin. thetank 11 becausel of the check valves 12. l

The present .embodiment of the invention, however, has'been disclosedindetail merely by"wa v. of example since in actual practice -it attains'the featr'esof advantage enumery,ated as desirable in the 'statementof.the', invention and the above descriptionl It will be apparent thatchanges in the details of construction, and in the combination andarrangement of parts may be resortedto Without departing from thespirit; or scope of the inventionr as hereinafter claimed or sacrificingany of its/advantages.

Having thus described my invention, what I claim as new is p 1. Incombination, an aeroplaney fuselage, a pipe leading from the front ofthe fuselage, a compressor connected with the pipe,

a. prime mover, means for operatively condiflerent directions, and thenrearwardly, valves in said last mentioned pipes, and means 'forsimultaneously operating the valves.

` 2. In an aeroplane havin a'fuselage, a tank in the rear of the fuseage, said tank adapted to store air under ressure, a plurality of pipesextending orwardly from the tank, then' laterally, in diierentdirections, and then rearwardly, valves in said p`pes, and means forsimultaneously operatin the valves.

n testimony whereof .I affix my signature. y

VINCENT CAVALERI.

